公开(公告)号：US12286927B2

公开(公告)日：2025-04-29

申请号：US17169889

申请日：2021-02-08

Applicant: General Electric Company

Inventor： Jeffrey Douglas Rambo ,  Brandon Wayne Miller ,  David Marion Ostdiek

IPC: F02C7/18 ,  F02C6/08 ,  F02C7/224 ,  F02C9/18 ,  F02C7/14

Abstract: A method for energy conversion for a vehicle is provided. The method including extracting a flow of compressed fluid from a compressor section of a propulsion system; flowing the flow of compressed fluid to a turbine operably coupled to a driveshaft, in which the driveshaft is operably coupled to a load device; expanding the flow of compressed fluid through the turbine to generate an output torque at the driveshaft to operate the load device; and flowing the expanded flow of compressed fluid from the turbine to thermal communication with a thermal load.

公开(公告)号：US12270340B2

公开(公告)日：2025-04-08

申请号：US18404364

申请日：2024-01-04

Applicant: General Electric Company

Inventor： Honggang Wang ,  Brandon Wayne Miller ,  Michael Anthony Benjamin ,  Richard L. Hart ,  Randy M. Vondrell ,  Ryan St. Pierre

IPC: F02C7/22 ,  H01M8/04089 ,  H01M8/04111 ,  H01M8/0612

Abstract: A gas turbine engine is provided. The gas turbine engine includes a turbomachine having a compressor section, a combustor, and a turbine section arranged in serial flow order, the turbomachine further including an outer casing and, during operation of the gas turbine engine, an exhaust gas flow from the turbine section; and a fuel cell assembly positioned within the outer casing of the turbomachine, the fuel cell assembly having a fuel cell defining an inlet positioned to receive a portion of the exhaust gas flow, an outlet positioned to provide output products directly to the exhaust gas flow, or both.

公开(公告)号：US12261334B2

公开(公告)日：2025-03-25

申请号：US18404083

申请日：2024-01-04

Applicant: General Electric Company

Inventor： Honggang Wang ,  Brandon Wayne Miller ,  Michael Anthony Benjamin ,  Richard L. Hart ,  Randy M. Vondrell ,  Ryan St. Pierre

IPC: H01M8/0612 ,  F02C7/22

Abstract: A gas turbine engine is provided. The gas turbine engine includes a turbomachine having a compressor section, a combustor, and a turbine section arranged in serial flow order, the turbomachine further including an outer casing; a fuel cell assembly positioned within the outer casing of the turbomachine, the fuel cell assembly including a fuel cell and an output products line in fluid communication with an outlet of the fuel cell for receiving output products from the fuel cell; a fuel delivery assembly including a fuel line; and a reformer in communication with the fuel line and the output products from the fuel cell during operation of the gas turbine engine to convert a fuel flow through the fuel line to a hydrogen rich gas.

公开(公告)号：US12173658B2

公开(公告)日：2024-12-24

申请号：US18085714

申请日：2022-12-21

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  John Carl Glessner ,  Lawrence William Nurre ,  Ian Francis Prentice ,  Ethan Patrick O'Connor ,  Arthur William Sibbach

IPC: F02C7/32 ,  F01D25/24 ,  F02C3/06

Abstract: A turbine engine that includes an engine core, an inner cowl, an outer cowl and an accessory gearbox. The engine core includes at least a compressor section, a combustion section, and a turbine section in axial flow arrangement. The accessory gearbox is operably coupled to the engine core and includes a first portion and a second portion.

公开(公告)号：US12134971B2

公开(公告)日：2024-11-05

申请号：US17213503

申请日：2021-03-26

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  Ian Francis Prentice ,  Daniel Alan Niergarth

IPC: F01D21/04 ,  B64C11/06 ,  F01D5/30 ,  F01D7/00 ,  F01D25/16 ,  F02C3/04 ,  F04D29/32 ,  F04D27/02

Abstract: A fan for a gas turbine engine is provided. The fan includes a plurality of fan blades, a disk, and a trunnion mechanism for attaching the fan blades to the disk. The disk can be formed of a plurality of individual disk segments, with the trunnion mechanism attaching one of the plurality of fan blades to a respective disk segment. A retention member is also provided. The retention member includes a means for catching a portion of the trunnion mechanism should a primary attachment system of the trunnion mechanism fail.

公开(公告)号：US12104499B2

公开(公告)日：2024-10-01

申请号：US18330000

申请日：2023-06-06

Applicant: General Electric Company

Inventor： Scott Alan Schimmels ,  Daniel Alan Niergarth ,  Arthur William Sibbach ,  Brandon Wayne Miller

IPC: F02C7/12 ,  F01D25/10 ,  F01D25/12

CPC classification number: F01D25/10 ,  F01D25/12 ,  F02C7/12 ,  F05D2220/32 ,  F05D2260/20 ,  F05D2260/213

Abstract: A method of regulating pressure in a thermal transport bus of a gas turbine engine, the method including: operating the gas turbine engine with the thermal transport bus having an intermediary heat exchange fluid flowing therethrough, the thermal transport bus including one or more heat source heat exchangers and one or more heat sink heat exchangers in thermal communication through the intermediary heat exchanger fluid; and adjusting a flow volume of the thermal transport bus using a variable volume device in fluid communication with the thermal transport bus in response to a pressure change associated with the thermal transport bus.

公开(公告)号：US12085019B2

公开(公告)日：2024-09-10

申请号：US18455137

申请日：2023-08-24

Applicant: General Electric Company

Inventor： Arthur William Sibbach ,  Brandon Wayne Miller

IPC: F02K3/00 ,  F02C6/20 ,  F02C7/04 ,  F02C7/05

CPC classification number: F02C7/05 ,  F02C6/20 ,  F02C7/04 ,  F02K3/00 ,  F05D2220/36

Abstract: A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of fan blades; a turbomachine operably coupled to the fan for driving the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath; a nacelle surrounding and at least partially enclosing the fan; an inlet pre-swirl feature located upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle; and a means for directing incoming objects towards an outer portion of the turbofan engine in communication with the inlet pre-swirl feature.

公开(公告)号：US12018594B2

公开(公告)日：2024-06-25

申请号：US18462064

申请日：2023-09-06

Applicant: General Electric Company

Inventor： Arthur William Sibbach ,  Aaron Michael Dziech ,  Scott Alan Schimmels ,  Robert R. Rachedi ,  Jeffrey Douglas Rambo ,  Brandon Wayne Miller

IPC: F02C7/224 ,  F01K23/02 ,  F01K25/10 ,  F02C3/22 ,  F02C3/30

CPC classification number: F01K23/02 ,  F01K25/103 ,  F02C3/22 ,  F02C3/30 ,  F02C7/224 ,  F05D2220/31 ,  F05D2220/32 ,  F05D2220/72 ,  F05D2220/74 ,  F05D2240/36 ,  F05D2260/213

Abstract: A pericritical fluid system for a thermal management system associated with a turbine engine may include one or more sensors configured to generate sensor outputs corresponding to one or more phase properties of a pericritical fluid flowing through a cooling circuit of the thermal management system, and a controller configured to generate control commands configured to control one or more controllable components of the thermal management system based at least in part on the sensor outputs. The one or more sensors may include one or more phase detection sensors, such as an acoustic sensor.

公开(公告)号：US11994066B2

公开(公告)日：2024-05-28

申请号：US17874358

申请日：2022-07-27

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  Kevin Edward Hinderliter ,  Daniel Alan Niergarth ,  Brian Gene Brzek

IPC: F02C7/12 ,  F02C7/06

CPC classification number: F02C7/12 ,  F02C7/06 ,  F05D2240/50 ,  F05D2260/20

Abstract: A thermal management system of a gas turbine engine, the thermal management system including: a thermal transport bus configured to have a heat exchange fluid flowing therethrough and including a pump including a plurality of bearings; an auxiliary thermal bus in thermal communication with the plurality of bearings; and an auxiliary heat exchanger in thermal communication with the auxiliary thermal bus.

公开(公告)号：US20240026901A1

公开(公告)日：2024-01-25

申请号：US18481584

申请日：2023-10-05

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  Arthur William Sibbach

IPC: F04D29/54 ,  F04D19/00

CPC classification number: F04D29/542 ,  F04D19/002

Abstract: A gas turbine engine includes a fan having a plurality of fan blades, a turbomachine operably coupled to the fan for driving the fan, the turbomachine including a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath, a nacelle surrounding and at least partially enclosing the fan, the nacelle defining a longitudinal axis, and an inlet pre-swirl feature located upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle, wherein the inlet pre-swirl feature is transitionable between a first angle with respect to the longitudinal axis of the nacelle and a second angle with respect to the longitudinal axis of the nacelle.